EP2811121B1 - Composite casing for axial turbomachine compressor with metal flange - Google Patents

Composite casing for axial turbomachine compressor with metal flange Download PDF

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Publication number
EP2811121B1
EP2811121B1 EP13170209.4A EP13170209A EP2811121B1 EP 2811121 B1 EP2811121 B1 EP 2811121B1 EP 13170209 A EP13170209 A EP 13170209A EP 2811121 B1 EP2811121 B1 EP 2811121B1
Authority
EP
European Patent Office
Prior art keywords
annular
housing
annular flange
platforms
flange
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13170209.4A
Other languages
German (de)
French (fr)
Other versions
EP2811121A1 (en
Inventor
Alain Derclaye
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Safran Aero Boosters SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Priority to EP13170209.4A priority Critical patent/EP2811121B1/en
Priority to CA2852180A priority patent/CA2852180A1/en
Priority to US14/285,013 priority patent/US20150192140A1/en
Priority to RU2014121327A priority patent/RU2674808C2/en
Priority to CN201410235799.2A priority patent/CN104213947B/en
Publication of EP2811121A1 publication Critical patent/EP2811121A1/en
Application granted granted Critical
Publication of EP2811121B1 publication Critical patent/EP2811121B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to an axial turbomachine casing. More particularly, the invention relates to an annular axial turbomachine compressor casing made of a composite material and supporting an annular row of blades.
  • a structuring element such as an outer annular casing can be made of composite material.
  • Such a casing in addition to supporting rows of stator vanes, generally serves as a mounting bracket for other structuring elements of the turbojet engine. It must therefore have adequate mechanical strength.
  • the housing In the case of a low pressure compressor housing, the housing is in contact with the separation spout. However, the latter is subject to ingestions. The housing must therefore have a certain flexibility and resilience to deform and withstand the impacts without breaking.
  • the blades which are fixed on the housing can be by means of platforms pressed against the inner surface of the housing.
  • the blades being subjected to efforts related to the flow flow, they transmit forces to which the housing must resist.
  • the casing must tolerate the clamping forces of the blade attachment means and the resulting stress concentrations. It should be noted that the casing is currently in contact with several sets of fixing means which also generate stress concentrations.
  • the document EP 2 402 615 A1 discloses an outer casing of axial turbomachine compressor.
  • the housing includes a wall annular and two radial flanges, one upstream and the other downstream.
  • the housing is made of a composite material. It supports several annular rows of stator vanes. Each blade has an external platform which is fixed to the annular wall by means of fixing means.
  • the document FR 2 282 537 A1 discloses a compressor with an axial turbomachine outer casing.
  • the housing includes annular rows of vanes as well as alternating annular spacers and blade retaining rings.
  • the retaining rings are made of metal, and are fitted in the annular spacers. These are made of light metal to cope with mechanical stresses.
  • the housing receives a composite annular wall that surrounds the retaining rings and the annular spacers.
  • the implementation of the composite wall is performed on a mandrel where are fitted the rings and spacers.
  • the use of the mandrel represents a significant cost both in terms of tools and in terms of manpower.
  • the winding time of the continuous filament on the mandrel is an expensive manufacturing time. Although this case includes composite, it remains heavy because of its metal elements.
  • the blade attachment mode is complex. It relies on a plurality of mechanical interfaces requiring expensive adjustments.
  • the invention aims to solve at least one of the technical problems raised by the prior art. More specifically, the invention aims to reduce the cost of producing a composite housing. The invention also aims to reduce the mechanical stresses in the composite annular wall of a turbomachine casing.
  • the subject of the invention is an axial turbomachine casing, in particular a compressor, according to claim 1.
  • annular flange attached to the annular wall means an annular flange fixed to the annular wall, for example by means of fixing means.
  • the radial section of the annular flange has an L-shaped profile, the profile comprising an axially extending portion and a radially extending portion, preferably the axially extending portion. is predominantly arranged radially on the side of the inner surface of the annular wall, and the radially extending portion is predominantly radially disposed on the side of the outer surface of the annular wall.
  • the portion of the axially extending flange comprises an edge delimiting the annular zone of reception of the platforms of the blades.
  • the annular wall comprises an annular zone for receiving an abradable material, the zone of receiving platforms being delimited, on one side, by said receiving area of an abradable material and, on the other side, by the edge of the axially extending flange portion.
  • the zone of reception of the platforms of the blades forms an annular cavity, preferably the radial section of the annular cavity is essentially rectangular and configured to allow a radial insertion of the platforms of the blades.
  • the annular wall and the annular flange are made of different materials, preferably the annular flange is made of a metallic material.
  • the composite annular wall comprises an organic matrix and a preform comprising fibers, preferably the matrix is distributed homogeneously on the annular wall.
  • the annular wall comprises first fastening means
  • the annular flange comprises second fastening means
  • the vanes comprise third fastening means
  • the first fastening means cooperate with the second fastening means and / or the third fastening means cooperate with both the first fastening means and the second fastening means.
  • the third attachment means extend radially and pass through the annular wall and the annular flange, preferably the third fixing means comprise clamping means, possibly reversible.
  • each platform has longitudinal edges and transverse edges, at least one of said edges being in contact with the annular flange, the flange thus ensuring a locking in rotation of the platforms.
  • the platforms and the annular flange each comprise a guide surface intended to guide a flow in the turbomachine, the guide surfaces of the platforms flush with the guide surface of the annular flange.
  • the annular flange comprises a portion which conforms to a surface, preferably an inner surface, of the annular wall, said portion extending axially over the majority of the receiving area of the blade platforms.
  • the annular flange comprises radial cavities intended to receive the platforms of the blades, preferably the radial cavities are configured to be mainly open towards the bodies of the blades.
  • the casing comprises an annular array of vanes with platforms which each have a central zone generally forming a disk, and two zones of lesser thickness arranged axially on either side of the central zone. , the central zone being predominantly in radial support against the annular flange and at least one of the thinner zone being predominantly in axial abutment against the annular flange.
  • the fixing means may comprise axes, preferably threaded, and may comprise clamping means.
  • the fixing means are reversible fixing means.
  • the radial section of the annular flange is a section made along a plane comprising a radial axis and the axis of rotation of the turbomachine.
  • the compressor is a low pressure compressor.
  • the casing is an outer casing adapted to guide an axial flow.
  • the housing comprises two half-shells separated along a longitudinal plane.
  • longitudinal plane means a plane passing through the axis of rotation of the turbomachine.
  • the housing comprises several annular rows of blades, preferably at least three.
  • the casing is a compressor casing comprising several annular rows of rotor blades, the casing surrounding the majority of rows of rotor blades.
  • the annular wall comprises a curved profile of revolution, preferably the profile of revolution is bent outwards.
  • the annular wall is made according to a resin injection method by transfer into a mold in which is contained a preform.
  • the means for fixing the annular wall comprise orifices.
  • the first fixing means comprise a first set of fixing means arranged annularly and axially overlapped by the annular flange, and a second set of fastening means arranged annularly and axially overlapped by the platforms. , the axial spacing between the first game and the second game being less than the axial length of the platforms.
  • the wall is predominantly non-metallic.
  • the wall is predominantly, preferably only consisting of a matrix and fibers.
  • the majority of the wall is the mass majority or the bulk majority.
  • the density of the wall is less than 4.00; preferably less than 2.50; more preferably less than 1.00.
  • the annular flange is made of titanium, aluminum or steel.
  • the annular flange extends radially predominantly in a direction opposite to the vanes with respect to the annular wall.
  • the fixing orifices of the annular flange are arranged in the radial cavities.
  • the annular flange has a junction portion between the radial portion and the axial portion.
  • the annular flange has an axial extension extending axially from the joining portion to the axial level of the bearing plane of the radial portion.
  • each radial cavity has a central part and two lateral parts arranged laterally in the continuity of the central part, the lateral parts being inclined with respect to the central part towards the outside of the central part. corresponding cavity.
  • the radial cavities are spaced from each other in a circumferential direction.
  • the radial portion has mounting means such as fixing orifices which extend generally axially.
  • the radial portion has a bearing surface perpendicular to the axis of rotation of the turbomachine.
  • the joining portion has a rectilinear profile and is inclined with respect to the radial portion and with respect to the axial portion, or the profile of the joining portion forms a step, preferably the portion of junction in the form of step has a cylindrical bearing adapted to ensure shaft shaft fitting.
  • the preform comprises a stack of sheets of carbon fibers and / or sheets of glass fibers, possibly the number of sheets remains equal over the entire surface of the preform.
  • the fibers measure more than 3.00 cm, preferably more than 6.00 cm, more preferably more than 12.00 cm.
  • the blades are arranged in rectifier segments having common platforms.
  • the invention also relates to an axial turbomachine casing comprising a casing, remarkable in that the casing is in accordance with the invention, preferably the casing is an outer annular casing and comprises an upstream annular flange and a downstream annular flange.
  • the invention entails a reduction in the cost of producing the composite casing with a metal flange. It proposes a modular composite housing architecture since it allows an isolated manufacture of the various elements. This technology also simplifies possible repairs.
  • the invention makes it possible to reduce the mechanical stresses in the annular wall of the casing. Indeed, the invention makes it possible to distribute a part of the forces on the surfaces of the platforms of the blades, the distribution being direct or indirect.
  • the invention proposes to add an interface between the blade platforms and the flange, which is a force transmission path that locally bypasses the edge of the annular wall.
  • the invention employs an annular flange with a material different from that of the annular wall.
  • the material of the blade platforms is also different from that of the annular flange.
  • the invention makes it possible to reduce the number of sheets of the composite preform by reducing the mechanical stresses.
  • One consequence is that the preform is simpler to achieve since the difficulty of implementation of the sheets tends to increase for each additional sheet. This difficulty is amplified by the surfaces curved that commonly presents a crankcase. An economy is realized on the costs of material and manpower related to the preform.
  • inner or inner and outer or outer refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • Reducing means can increase the speed of rotation transmitted to the compressors.
  • the different turbine stages can each be connected to the compressor stages via concentric shafts.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes. Rotation of the rotor about its axis of rotation 14 thus allows to generate an air flow and to compress it gradually to the inlet of the combustion chamber 10.
  • a commonly designated fan inlet fan 16 is coupled to the rotor 12 and generates a flow of air which is divided into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical walls or ferrules which may be internal or external.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine.
  • the compressor may be a low-pressure compressor 4 such as that of the figure 1 .
  • the rotor 12 comprises several rows of rotor blades 24, in this case three.
  • the compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.
  • the rectifiers are associated with the fan 16 or a row of rotor vanes to straighten the air flow, so that convert the speed of the flow into pressure.
  • the stator vanes 26 extend essentially radially. They are regularly spaced from each other, and have the same angular orientation in the flow.
  • the blades 26 of the same row are identical.
  • the spacing between the blades may vary locally as well as their angular orientation. Some blades may be different from the rest of the blades in their row.
  • the stator vanes 26 each have a body also called blade, extending radially through the vein of the primary flow 18. Each blade also has at least one platform, possibly two platforms, namely an external platform 28 and an internal platform. Platforms radially delineate the flow primary. They comprise guide surfaces capable of guiding said flow.
  • the compressor has an outer annular housing 30.
  • the housing 30 envelopes the compressor. It has for this purpose an annular wall 32 surrounding the majority of the rotor blades 24.
  • the annular wall 32 may be formed of two half-shells each forming a half of an axially cut tube.
  • the annular wall 32 has a shape of barrel or ogive. Its inner surface is concave. Its radius variation is continuous to gradually compress the flow.
  • the outer casing 30 is attached upstream to the separation spout 22, and is received by the intermediate casing 34 of the downstream turbomachine.
  • the intermediate casing 34 comprises an inner annular wall and an outer annular wall between which radially extends an annular row of blades or casing arms.
  • the casing is essentially, preferably only connected to the separation spout 22 and the intermediate casing.
  • the separation spout 22 can only be fixed to the outer casing 30 so as to be its sole support.
  • the outer casing 30 also comprises a radial annular flange, preferably two annular flanges 36.
  • the outer casing 30 is fixed to the partition spout 22 and to the intermediate casing 34 via its annular flanges 36.
  • the outer casing 30 comprises a flange annular upstream and a downstream annular flange. Each of them can form a semicircle. Preferably, each semicircle coincides with a half-shell of the outer casing 30.
  • the outer casing 30 also comprises annular layers of abradable material 38. These abradable layers 38 are arranged axially in line with the rotor vanes 24. They extend axially between the outer platforms 28 of the stator vanes 26.
  • the figure 3 is a sectional view of an outer compressor casing 30 of an axial turbomachine 2 such as that of the figure 1 .
  • the teaching of the invention could also be applied to a turbine casing, a combustion chamber or an intermediate casing.
  • the casing may be an outer casing or an inner casing which delimits the outside, respectively inside an annular flow.
  • the casing shown shows one of the stator vanes 26 and a portion of the annular flange 36.
  • the annular wall 32 comprises first fixing means.
  • the first fastening means may comprise through orifices which form at least one annular row.
  • the first fastening means may comprise a first set of fastening means arranged annularly and a second set of fastening means arranged annularly.
  • the first set is axially overlapped by the annular flange, the second set being axially overlapped by the platform.
  • the first fastening means may comprise other sets of fastening means which are overlapped and cooperate with another radial annular flange and / or with other annular rows of vanes.
  • the annular wall 32 is made of composite material.
  • the composite material may comprise an organic matrix.
  • the matrix can be made from an organic resin injected into a mold and then polymerizing.
  • the injection process may be a transfer method, known by the acronym RTM (Resin Transfer Molding).
  • RTM Resin Transfer Molding
  • the resin is thermosetting. It can be an epoxy resin.
  • the composite material comprises a preform.
  • the latter may be formed of a stack of folds or sheets of fibers.
  • the sheets can be sheets with glass fibers and / or sheets with carbon fibers.
  • the fibers are long fibers.
  • the fibers may be ordered fibers and / or randomly arranged fibers.
  • the fibers are woven. They can be pre-impregnated with a resin.
  • the preform comprises a stack of 5 to 40 leaves, preferably 8 to 20 leaves, more preferably 10 to 15 leaves.
  • the number of layers formed by the sheets may vary locally so as to locally reinforce the housing, for example at the fixing areas.
  • the annular flange 36 is made of a material different from the annular wall 32. It may be made of a metallic material. It can be made of titanium, aluminum or steel.
  • the ring flange can be made of a composite material, for example ceramic matrix and / or with metal fibers. The matrices and fibers presented above can also be used.
  • the annular flange 36 generally has an "L" profile.
  • the profile has a radial portion 40 and an axial portion 42.
  • the profile generally has a constant thickness, its thickness varies less than 20% relative to its average thickness.
  • the axial portion 42 may be inclined relative to the axis of rotation of the turbomachine.
  • the axial portion 42 has a bearing surface conforming to the inner surface of the end of the annular wall 32.
  • the inner surface of the annular wall 32 comprises an annular receiving zone 43 of the blade platforms 26.
  • the annular receiving zone 43 may have a rectangular radial profile, or substantially trapezoidal shape so as to allow the insertion of the platforms from inside.
  • the annular flange 36 may define directly the annular receiving zone 43.
  • it is the axial portion 42 which delimits the annular receiving zone 43.
  • it has an upstream annular edge 44 which delimits the zone of
  • the annular wall 32 comprises an annular zone for receiving an abradable material 37.
  • the reception zone of the platforms 43 may be delimited by the annular zone for receiving an abradable material 37. It may also be the edge 44 of the axially extending flange portion 42.
  • the annular abradable layer 38 is housed in the annular zone for receiving an abradable material 37.
  • the annular flange 36 is fixed to the end of the annular wall 32 via its axial portion 42.
  • the latter has for this purpose second fastening means 45 which cooperate with first means for fixing the wall.
  • the second fixing means 45 may be axes extending generally radially, preferably orthogonal to the interface between the annular wall 32 and the axial portion 42.
  • the axes may be lockbolts or screws. They are mounted on the annular flange once it is pressed against the annular wall.
  • the radial portion 40 of the profile of the annular flange 36 generates by rotation about the axis of rotation 14 a perpendicular plane 46 to the same axis.
  • Mounting means 48 may be placed on the radial portion 40.
  • the mounting means 48 may be openings for receiving fastening screws which cooperate with the intermediate casing.
  • the second fixing means 45 may be less spaced apart from each other than the mounting means 48.
  • the profile of the annular flange optionally comprises a joining portion 50 between the axial portion 42 and the radial portion 40.
  • the joining portion 50 may have a step shape.
  • the step form may provide an axial clearance 52 at the axial end of the annular wall 32.
  • the clearance 52 may be zero so as to provide support.
  • Preferably the step form protrudes outwardly.
  • the inner surface of the junction zone 50 may rotatably generate a cylindrical surface 54. This cylindrical surface 54 may form a bore shaft bore with the partition spout, intermediate housing, or any other element to which the annular flange 36 is attached. .
  • the blade 26 has third fixing means 56 for mounting it on the annular wall 32.
  • the third fastening means 56 cooperate with the first fixing means of the annular wall.
  • the third attachment means 56 extend radially from the platform 28 in a direction opposite to the blade of the blade 26.
  • the third attachment means 56 can pass through the annular wall 32.
  • the platform 28 generally marries the inner surface of the annular wall.
  • the platform has a bearing surface which is generally pressed against the annular wall, possibly only the contour of the bearing surface is in contact with the annular wall.
  • the platform 28 is in contact with the axial portion 42 of the annular flange. They abut axially against each other. Since the annular wall is inclined at this point, the platform and the axial portion of the annular flange also allow radially oriented transmission of force. The annular flange and the annular wall are in contact with the level of the axial portion 42. This contact area is extended and also allows transmission of axial and radial forces.
  • the junction 58 between the axial portion 42 and the platform 28 is smooth. At this point, the thicknesses of the axial portion and the annular flange are equal so as not to disturb the flow. To avoid overlap, the profile of the interface extends perpendicularly to the surface of the annular wall. The two elements are in contact over their entire thickness to promote the transmission of efforts.
  • the figure 4 represents a housing 130 according to a second embodiment of the invention. This figure 4 resumes the numbering of the preceding figures for identical or similar elements, however, the numbering is incremented by 100. Specific numbers are used for the specific elements of this embodiment.
  • the joining portion 150 has a straight profile.
  • the profile of the joining portion is inclined relative to the profiles of the axial portion and the radial portion.
  • the length of the axial portion 142 is greater than the length of the platform 128.
  • the axial portion extends beyond the platform upstream and downstream.
  • the annular flange 136 has a radial cavity 160 in which is introduced the platform 128 of the blade 126.
  • the radial cavity 160 may be formed on the inner surface of the axial portion when the latter is placed inside the annular wall . According to another configuration, the radial cavity 160 may be formed on the outer surface if the axial portion is placed outside the annular wall.
  • the blade 126 is mounted on the annular flange 136 by inserting its platform 128 into the radial cavity 160 from the inside.
  • the platform 128 has a central zone 162 conforming to the bottom of the radial cavity 160. It also has thinner zones 164 arranged axially on either side of the central zone 162. The zones of smaller thickness 164 may be set back from the bottom of the radial cavity 160.
  • the third attachment means 156 of the blade, the second fixing means of the annular flange, and the first fastening means of the annular wall coincide.
  • the third attachment means 156 cooperate with both the first attachment means and the second attachment means.
  • the orifices formed in the annular flange and the orifices formed at the ends of the annular wall are matched.
  • the attachment axis 156 of the vane passes through the fixing orifice of the annular wall and the fixing orifice of the annular flange.
  • the annular flange 136 also has an axial extension 166.
  • the axial extension 166 extends from the junction portion 150 in a direction opposite to the axial portion 142.
  • the axial extension may extend up to the right of the downstream surface. the radial portion 140. It can serve as an axial stop.
  • the figure 5 represents the guide surface of the annular flange according to the second embodiment of the invention.
  • the annular flange 136 shows a plurality of radial cavities 160.
  • the radial cavities are arranged annularly. They are distributed on the inner surface of the annular flange 136.
  • the radial cavities 160 are identical. They each have a second fixing means.
  • a platform 128 of blade 126 is shown introduced into a radial cavity.
  • Each radial cavity 160 receives a blade platform 128.
  • the length of the radial cavity is adjusted to the length of the platform so as to axially wedge the platform in the housing.
  • each radial cavity 160 has a central portion 168 and two lateral portions 170 arranged axially in the extension of the central portion 168. These parts are flat. Each side portion is inclined relative to the central portion outwardly of the corresponding cavity.
  • the figure 6 represents a platform 128 of dawn 126 according to the second embodiment of the invention.
  • this platform model may be employed in other embodiments of the invention.
  • the platform 128 has a generally rectangular shape. It has two longitudinal sides 172 opposite and arranged along the axis of rotation of the turbomachine, and two opposite transverse sides 174 which are arranged perpendicularly to the axis of rotation of the turbomachine.
  • the central portion 162 of the platform has a general shape of disc.
  • the disk may be truncated, possibly on both longitudinal sides 172.
  • the third attachment means 156 are advantageously centered on the central portion 162. Creating a platform with a reduced bearing surface makes it possible to reduce the friction surface between the platform and the annular flange. This facilitates the angular positioning of the dawn. Also, the smaller areas 164 can lighten the dawn.

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  • Engineering & Computer Science (AREA)
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Description

Domaine techniqueTechnical area

L'invention a trait à un carter de turbomachine axiale. Plus particulièrement, l'invention a trait à un carter annulaire de compresseur de turbomachine axiale réalisé en un matériau composite et supportant une rangée annulaire d'aubes.The invention relates to an axial turbomachine casing. More particularly, the invention relates to an annular axial turbomachine compressor casing made of a composite material and supporting an annular row of blades.

Technique antérieurePrior art

Dans l'optique de réduire la masse d'un turboréacteur d'aéronef, certains éléments sont réalisés en matériaux composites. En particuliers, un élément structurant comme un carter annulaire extérieur peut être réalisé en matériau composite. Un tel carter, en plus de supporter des rangées d'aubes statoriques, sert généralement de support de montage pour d'autres éléments structurant du turboréacteur. Il doit par conséquent présenter une résistance mécanique adéquate.In order to reduce the mass of an aircraft turbojet engine, certain elements are made of composite materials. In particular, a structuring element such as an outer annular casing can be made of composite material. Such a casing, in addition to supporting rows of stator vanes, generally serves as a mounting bracket for other structuring elements of the turbojet engine. It must therefore have adequate mechanical strength.

Lorsqu'il s'agit d'un carter de compresseur basse pression, le carter est en contact du bec de séparation. Or, ce dernier est soumis à des ingestions. Le carter doit donc présenter une certaine souplesse et une certaine résilience pour se déformer et supporter les impacts sans rompre.In the case of a low pressure compressor housing, the housing is in contact with the separation spout. However, the latter is subject to ingestions. The housing must therefore have a certain flexibility and resilience to deform and withstand the impacts without breaking.

Les aubes qui sont fixées sur le carter peuvent l'être par l'intermédiaire de plateformes plaquées contre la surface intérieure du carter. Les aubes étant soumises à des efforts liés à l'écoulement du flux, elles transmettent des efforts auquel le carter doit résister. En complément, le carter doit tolérer les efforts de serrage des moyens de fixation des aubes ainsi que les concentrations de contraintes qui en découlent. Il est à souligner que le carter est couramment en contact de plusieurs jeux de moyens de fixations qui engendrent également des concentrations de contraintes.The blades which are fixed on the housing can be by means of platforms pressed against the inner surface of the housing. The blades being subjected to efforts related to the flow flow, they transmit forces to which the housing must resist. In addition, the casing must tolerate the clamping forces of the blade attachment means and the resulting stress concentrations. It should be noted that the casing is currently in contact with several sets of fixing means which also generate stress concentrations.

Le document EP 2 402 615 A1 divulgue un carter externe de compresseur de turbomachine axiale. Le carter comprend une paroi annulaire et deux brides radiales, l'une en amont et l'autre en aval. Le carter est réalisé en un matériau composite. Il supporte plusieurs rangées annulaires d'aubes statoriques. Chaque aube présente une plateforme externe qui est fixée à la paroi annulaire à l'aide de moyens de fixation.The document EP 2 402 615 A1 discloses an outer casing of axial turbomachine compressor. The housing includes a wall annular and two radial flanges, one upstream and the other downstream. The housing is made of a composite material. It supports several annular rows of stator vanes. Each blade has an external platform which is fixed to the annular wall by means of fixing means.

Il est connu de fixer les brides radiales sur un bec de séparation et sur un carter intermédiaire de la turbomachine. Ces fixations peuvent s'effectuer à l'aide de boulons insérés dans des orifices ménagés dans les brides radiales. Ces orifices sont particulièrement sollicités lors du fonctionnement de la turbomachine, des arrachements peuvent se produire en raison des efforts mécaniques de serrage et/ou des vibrations.It is known to fix the radial flanges on a separation spout and on an intermediate casing of the turbomachine. These fasteners can be made using bolts inserted into holes in the radial flanges. These orifices are particularly stressed during operation of the turbomachine, tearing may occur due to mechanical clamping forces and / or vibrations.

Pour contrer ces arrachements, il est envisageable d'épaissir fortement les brides. Or, cette solution tend à alourdir le carter, ce qui va à l'encontre du gain de masse espéré via la solution composite. De plus, la résistance mécanique de cette solution reste limitée et les concentrations de contraintes subsistent.To counter these cuts, it is possible to thicken the flanges. However, this solution tends to increase the casing, which goes against the mass gain expected via the composite solution. In addition, the mechanical strength of this solution remains limited and the stress concentrations remain.

Afin de renforcer la paroi, il est connu de réaliser un carter annulaire avec une paroi composite et des brides radiales métalliques.In order to reinforce the wall, it is known to produce an annular casing with a composite wall and radial metal flanges.

Le document FR 2 282 537 A1 divulgue un compresseur avec un carter externe de turbomachine axiale. Le carter comprend des rangées annulaires d'aubes ainsi qu'une alternance d'entretoises annulaires et d'anneaux de retenue d'aubes. Les anneaux de retenue sont réalisés en métal, et sont emmanchés dans les entretoises annulaires. Celles-ci sont réalisées en métal léger pour faire face aux contraintes mécaniques. Le carter reçoit une paroi annulaire en composite qui entoure les anneaux de retenue et les entretoises annulaires. La mise en oeuvre de la paroi composite s'effectue sur un mandrin où sont emmanchés les anneaux et les entretoises. L'emploi du mandrin représente un coût important à la fois en termes d'outillage et en termes de main d'oeuvre. Le temps d'enroulement du filament continu sur le mandrin constitue un temps de fabrication dispendieux. Bien que ce carter comprenne du composite, il reste lourd en raison de ses éléments métalliques. De plus, le mode de fixation des aubes est complexe. Il repose sur une pluralité d'interfaces mécaniques nécessitant des ajustements onéreux.The document FR 2 282 537 A1 discloses a compressor with an axial turbomachine outer casing. The housing includes annular rows of vanes as well as alternating annular spacers and blade retaining rings. The retaining rings are made of metal, and are fitted in the annular spacers. These are made of light metal to cope with mechanical stresses. The housing receives a composite annular wall that surrounds the retaining rings and the annular spacers. The implementation of the composite wall is performed on a mandrel where are fitted the rings and spacers. The use of the mandrel represents a significant cost both in terms of tools and in terms of manpower. The winding time of the continuous filament on the mandrel is an expensive manufacturing time. Although this case includes composite, it remains heavy because of its metal elements. In addition, the blade attachment mode is complex. It relies on a plurality of mechanical interfaces requiring expensive adjustments.

Le document US 2009/0175719 A1 divulgue un carter conforme au préambule de la revendication 1.The document US 2009/0175719 A1 discloses a housing according to the preamble of claim 1.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

L'invention a pour objectif de résoudre au moins un des problèmes techniques soulevés par l'art antérieur. Plus précisément, l'invention a pour objectif de réduire le coût de réalisation d'un carter composite. L'invention a également pour objectif de réduire les contraintes mécaniques dans la paroi annulaire en composite d'un carter de turbomachine.The invention aims to solve at least one of the technical problems raised by the prior art. More specifically, the invention aims to reduce the cost of producing a composite housing. The invention also aims to reduce the mechanical stresses in the composite annular wall of a turbomachine casing.

Solution techniqueTechnical solution

L'invention a pour objet un carter de turbomachine axiale, notamment de compresseur, selon la revendication 1.The subject of the invention is an axial turbomachine casing, in particular a compressor, according to claim 1.

On entend par bride annulaire rapportée sur la paroi annulaire une bride annulaire fixée sur la paroi annulaire, par exemple à l'aide de moyens de fixation.An annular flange attached to the annular wall means an annular flange fixed to the annular wall, for example by means of fixing means.

Suivant un mode avantageux de l'invention, la section radiale de la bride annulaire présente un profil en forme de « L », le profil comportant une portion s'étendant axialement et une portion s'étendant radialement, préférentiellement la portion s'étendant axialement est majoritairement disposée radialement du côté de la surface intérieure de la paroi annulaire, et la portion s'étendant radialement est majoritairement disposée radialement du côté de la surface extérieure de la paroi annulaire.According to an advantageous embodiment of the invention, the radial section of the annular flange has an L-shaped profile, the profile comprising an axially extending portion and a radially extending portion, preferably the axially extending portion. is predominantly arranged radially on the side of the inner surface of the annular wall, and the radially extending portion is predominantly radially disposed on the side of the outer surface of the annular wall.

Suivant un mode avantageux de l'invention, la portion de la bride s'étendant axialement comprend un bord délimitant la zone annulaire de réception des plateformes des aubes.According to an advantageous embodiment of the invention, the portion of the axially extending flange comprises an edge delimiting the annular zone of reception of the platforms of the blades.

Suivant un mode avantageux de l'invention, la paroi annulaire comprend une zone annulaire de réception d'un matériau abradable, la zone de réception des plateformes étant délimitée, d'un côté, par ladite zone de réception d'un matériau abradable et, de l'autre côté, par le bord de la portion de bride s'étendant axialement.According to an advantageous embodiment of the invention, the annular wall comprises an annular zone for receiving an abradable material, the zone of receiving platforms being delimited, on one side, by said receiving area of an abradable material and, on the other side, by the edge of the axially extending flange portion.

Suivant un mode avantageux de l'invention, la zone de réception des plateformes des aubes forme une cavité annulaire, préférentiellement la section radiale de la cavité annulaire est essentiellement rectangulaire et configurée pour permettre une insertion radiale des plateformes des aubes.According to an advantageous embodiment of the invention, the zone of reception of the platforms of the blades forms an annular cavity, preferably the radial section of the annular cavity is essentially rectangular and configured to allow a radial insertion of the platforms of the blades.

Suivant un mode avantageux de l'invention, la paroi annulaire et la bride annulaire sont réalisées en des matériaux différents, préférentiellement la bride annulaire est réalisée en un matériau métallique.According to an advantageous embodiment of the invention, the annular wall and the annular flange are made of different materials, preferably the annular flange is made of a metallic material.

Suivant un mode avantageux de l'invention, la paroi annulaire composite comporte une matrice organique et une préforme comprenant des fibres, préférentiellement la matrice est répartie de manière homogène sur la paroi annulaire.According to an advantageous embodiment of the invention, the composite annular wall comprises an organic matrix and a preform comprising fibers, preferably the matrix is distributed homogeneously on the annular wall.

Suivant un mode avantageux de l'invention, la paroi annulaire comprend des premiers moyens de fixation, la bride annulaire comprend des deuxièmes moyens de fixation et les aubes comprennent des troisièmes moyens de fixation, les premiers moyens de fixation coopèrent avec les deuxièmes moyens de fixation, et/ou les troisièmes moyens de fixation coopèrent à la fois avec les premiers moyens de fixation et les deuxièmes moyens de fixation.According to an advantageous embodiment of the invention, the annular wall comprises first fastening means, the annular flange comprises second fastening means and the vanes comprise third fastening means, the first fastening means cooperate with the second fastening means and / or the third fastening means cooperate with both the first fastening means and the second fastening means.

Suivant un mode avantageux de l'invention, les troisièmes moyens de fixation s'étendent radialement et traversent la paroi annulaire et la bride annulaire, préférentiellement les troisièmes moyens de fixation comprennent des moyens de serrage, éventuellement réversibles.According to an advantageous embodiment of the invention, the third attachment means extend radially and pass through the annular wall and the annular flange, preferably the third fixing means comprise clamping means, possibly reversible.

Suivant un mode avantageux de l'invention, le contour de chaque plateforme présente des bords longitudinaux et des bords transversaux, au moins un desdits bords étant en contact de la bride annulaire, la bride assurant ainsi un blocage en rotation des plateformes.According to an advantageous embodiment of the invention, the contour of each platform has longitudinal edges and transverse edges, at least one of said edges being in contact with the annular flange, the flange thus ensuring a locking in rotation of the platforms.

Suivant un mode avantageux de l'invention, les plateformes et la bride annulaire comprennent chacune une surface de guidage destinée à guider un flux dans la turbomachine, les surfaces de guidage des plateformes affleurant la surface de guidage de la bride annulaire.According to an advantageous embodiment of the invention, the platforms and the annular flange each comprise a guide surface intended to guide a flow in the turbomachine, the guide surfaces of the platforms flush with the guide surface of the annular flange.

Suivant un mode avantageux de l'invention, la bride annulaire comprend une partie qui épouse une surface, préférentiellement intérieure, de la paroi annulaire, ladite partie s'étendant axialement sur la majorité de la zone de réception des plateformes des aubes.According to an advantageous embodiment of the invention, the annular flange comprises a portion which conforms to a surface, preferably an inner surface, of the annular wall, said portion extending axially over the majority of the receiving area of the blade platforms.

Suivant un mode avantageux de l'invention, la bride annulaire comporte des cavités radiales destinées à recevoir les plateformes des aubes, préférentiellement les cavités radiales sont configurées pour être majoritairement ouvertes vers les corps des aubes.According to an advantageous embodiment of the invention, the annular flange comprises radial cavities intended to receive the platforms of the blades, preferably the radial cavities are configured to be mainly open towards the bodies of the blades.

Suivant un mode avantageux de l'invention, le carter comprend une rangée annulaire d'aubes avec des plateformes qui présentent chacune une zone centrale formant généralement un disque, et deux zones de moindre épaisseur disposées axialement de part et d'autre de la zone centrale, la zone centrale étant majoritairement en appui radial contre la bride annulaire et au moins une des zone de moindre épaisseur étant majoritairement en butée axiale contre la bride annulaire.According to an advantageous embodiment of the invention, the casing comprises an annular array of vanes with platforms which each have a central zone generally forming a disk, and two zones of lesser thickness arranged axially on either side of the central zone. , the central zone being predominantly in radial support against the annular flange and at least one of the thinner zone being predominantly in axial abutment against the annular flange.

Suivant un mode avantageux de l'invention, les moyens de fixation peuvent comprendre des axes, préférentiellement filetés, et peuvent comprendre des moyens de serrage.According to an advantageous embodiment of the invention, the fixing means may comprise axes, preferably threaded, and may comprise clamping means.

Suivant un mode avantageux de l'invention, les moyens de fixation sont des moyens de fixation réversibles.According to an advantageous embodiment of the invention, the fixing means are reversible fixing means.

La section radiale de la bride annulaire est une section réalisée suivant un plan comprenant un axe radial et l'axe de rotation de la turbomachine.The radial section of the annular flange is a section made along a plane comprising a radial axis and the axis of rotation of the turbomachine.

Suivant un mode avantageux de l'invention, le compresseur est un compresseur basse pression.According to an advantageous embodiment of the invention, the compressor is a low pressure compressor.

Suivant un mode avantageux de l'invention, le carter est un carter externe apte à guider un flux axial.According to an advantageous embodiment of the invention, the casing is an outer casing adapted to guide an axial flow.

Suivant un mode avantageux de l'invention, le carter comprend deux demi-coquilles séparées selon un plan longitudinal.According to an advantageous embodiment of the invention, the housing comprises two half-shells separated along a longitudinal plane.

Par plan longitudinal, on entend un plan passant par l'axe de rotation de la turbomachine.In longitudinal plane means a plane passing through the axis of rotation of the turbomachine.

Suivant un mode avantageux de l'invention, le carter comprend plusieurs rangées annulaires d'aubes, préférentiellement au moins trois.According to an advantageous embodiment of the invention, the housing comprises several annular rows of blades, preferably at least three.

Suivant un mode avantageux de l'invention, le carter est un carter de compresseur comprenant plusieurs rangées annulaires d'aubes rotoriques, le carter entourant la majorité des rangées d'aubes rotoriques.According to an advantageous embodiment of the invention, the casing is a compressor casing comprising several annular rows of rotor blades, the casing surrounding the majority of rows of rotor blades.

Suivant un mode avantageux de l'invention, la paroi annulaire comprend un profil de révolution courbe, préférentiellement le profil de révolution est coudé vers l'extérieur.According to an advantageous embodiment of the invention, the annular wall comprises a curved profile of revolution, preferably the profile of revolution is bent outwards.

Suivant un mode avantageux de l'invention, la paroi annulaire est réalisée selon un procédé d'injection de résine par transfert dans un moule dans lequel est renfermé une préforme.According to an advantageous embodiment of the invention, the annular wall is made according to a resin injection method by transfer into a mold in which is contained a preform.

Suivant un mode avantageux de l'invention, les moyens de fixation de la paroi annulaire comprennent des orifices.According to an advantageous embodiment of the invention, the means for fixing the annular wall comprise orifices.

Suivant un mode avantageux de l'invention, les premiers moyens de fixation comprennent un premier jeu de moyens de fixation disposés annulairement et chevauchés axialement par la bride annulaire, ainsi qu'un deuxième jeu de moyens de fixation disposés annulairement et chevauchés axialement par les plateformes, l'espacement axial entre le premier jeu et le deuxième jeu étant inférieur à la longueur axiale des plateformes.According to an advantageous embodiment of the invention, the first fixing means comprise a first set of fixing means arranged annularly and axially overlapped by the annular flange, and a second set of fastening means arranged annularly and axially overlapped by the platforms. , the axial spacing between the first game and the second game being less than the axial length of the platforms.

Suivant un mode avantageux de l'invention, la paroi est majoritairement non métallique.According to an advantageous embodiment of the invention, the wall is predominantly non-metallic.

Suivant un mode avantageux de l'invention, la paroi est majoritairement, préférentiellement uniquement constituée d'une matrice et de fibres.According to an advantageous embodiment of the invention, the wall is predominantly, preferably only consisting of a matrix and fibers.

La majorité de la paroi est la majorité massique ou la majorité volumique.The majority of the wall is the mass majority or the bulk majority.

Suivant un mode avantageux de l'invention, la densité de la paroi est inférieure à 4,00 ; préférentiellement inférieure à 2,50 ; plus préférentiellement inférieure à 1,00.According to an advantageous embodiment of the invention, the density of the wall is less than 4.00; preferably less than 2.50; more preferably less than 1.00.

Suivant un mode avantageux de l'invention, la bride annulaire est réalisée en titane, en aluminium ou en acier.According to an advantageous embodiment of the invention, the annular flange is made of titanium, aluminum or steel.

Suivant un mode avantageux de l'invention, la bride annulaire s'étend radialement majoritairement dans un sens opposé aux aubes par rapport à la paroi annulaire.According to an advantageous embodiment of the invention, the annular flange extends radially predominantly in a direction opposite to the vanes with respect to the annular wall.

Suivant un mode avantageux de l'invention, les orifices de fixation de la bride annulaire sont disposés dans les cavités radiales.According to an advantageous embodiment of the invention, the fixing orifices of the annular flange are arranged in the radial cavities.

Suivant un mode avantageux de l'invention, la bride annulaire présente une portion de jonction entre la portion radiale et la portion axiale.According to an advantageous embodiment of the invention, the annular flange has a junction portion between the radial portion and the axial portion.

Suivant un mode avantageux de l'invention, la bride annulaire présente un prolongement axial s'étendant axialement depuis la portion de jonction jusqu'au niveau axial du plan d'appui de la portion radiale.According to an advantageous embodiment of the invention, the annular flange has an axial extension extending axially from the joining portion to the axial level of the bearing plane of the radial portion.

Suivant un mode avantageux de l'invention, le fond de chaque cavité radiale présente une partie centrale et deux parties latérales disposées latéralement dans la continuité de la partie centrale, les parties latérales étant inclinées par rapport à la partie centrale vers l'extérieur de la cavité correspondante.According to an advantageous embodiment of the invention, the bottom of each radial cavity has a central part and two lateral parts arranged laterally in the continuity of the central part, the lateral parts being inclined with respect to the central part towards the outside of the central part. corresponding cavity.

Suivant un mode avantageux de l'invention, les cavités radiales sont distantes les unes des autres suivant une direction circonférentielle.According to an advantageous embodiment of the invention, the radial cavities are spaced from each other in a circumferential direction.

Suivant un mode avantageux de l'invention, la portion radiale présente des moyens de montage tels des orifices de fixation qui s'étendent généralement axialement.According to an advantageous embodiment of the invention, the radial portion has mounting means such as fixing orifices which extend generally axially.

Suivant un mode avantageux de l'invention, la portion radiale présente une surface d'appui perpendiculaire à l'axe de rotation de la turbomachine.According to an advantageous embodiment of the invention, the radial portion has a bearing surface perpendicular to the axis of rotation of the turbomachine.

Suivant un mode avantageux de l'invention, la portion de jonction présente un profil rectiligne et est incliné par rapport à la portion radiale et par rapport à la portion axiale, ou le profil de la portion de jonction forme une marche, préférentiellement la portion de jonction en forme de marche présente une portée cylindrique apte à assurer à emmanchement arbre alésage.According to an advantageous embodiment of the invention, the joining portion has a rectilinear profile and is inclined with respect to the radial portion and with respect to the axial portion, or the profile of the joining portion forms a step, preferably the portion of junction in the form of step has a cylindrical bearing adapted to ensure shaft shaft fitting.

Suivant un mode avantageux de l'invention, la préforme comporte un empilement de feuilles de fibres de carbone et/ou de feuilles de fibres de verre, éventuellement le nombre de feuilles reste égal sur toute la surface de la préforme.According to an advantageous embodiment of the invention, the preform comprises a stack of sheets of carbon fibers and / or sheets of glass fibers, possibly the number of sheets remains equal over the entire surface of the preform.

Suivant un mode avantageux de l'invention, les fibres mesurent plus de 3,00 cm, préférentiellement plus de 6,00 cm, encore plus préférentiellement plus de 12,00 cm.According to an advantageous embodiment of the invention, the fibers measure more than 3.00 cm, preferably more than 6.00 cm, more preferably more than 12.00 cm.

Suivant un mode avantageux de l'invention, les aubes sont disposées dans des segments de redresseur présentant des plateformes communes.According to an advantageous embodiment of the invention, the blades are arranged in rectifier segments having common platforms.

L'invention a également trait à un carter de turbomachine axiale comprenant un carter, remarquable en ce que le carter est conforme à l'invention, préférentiellement le carter est un carter annulaire externe et comprend une bride annulaire amont et une bride annulaire aval.The invention also relates to an axial turbomachine casing comprising a casing, remarkable in that the casing is in accordance with the invention, preferably the casing is an outer annular casing and comprises an upstream annular flange and a downstream annular flange.

Avantages apportésBenefits brought

L'invention entraine une réduction du coût de réalisation du carter composite avec une bride métallique. Elle propose une architecture de carter composite modulable puisqu'elle autorise une fabrication isolée des différents éléments. Cette technologie simplifie en outre d'éventuelles réparations.The invention entails a reduction in the cost of producing the composite casing with a metal flange. It proposes a modular composite housing architecture since it allows an isolated manufacture of the various elements. This technology also simplifies possible repairs.

L'invention permet de réduire les contraintes mécaniques dans la paroi annulaire du carter. En effet, l'invention permet de répartir une partie des efforts sur les surfaces des plateformes des aubes, la répartition étant directe ou indirecte. L'invention propose de rajouter une interface entre les plateformes d'aube et la bride, ce qui constitue une voie de transmission d'effort qui contourne localement le bord de la paroi annulaire.The invention makes it possible to reduce the mechanical stresses in the annular wall of the casing. Indeed, the invention makes it possible to distribute a part of the forces on the surfaces of the platforms of the blades, the distribution being direct or indirect. The invention proposes to add an interface between the blade platforms and the flange, which is a force transmission path that locally bypasses the edge of the annular wall.

L'invention emploie une bride annulaire avec un matériau différent de celui de la paroi annulaire. Le matériau des plateformes des aubes est également différent de celui de la bride annulaire. Ces particularités offrent une liberté de choix de matériaux présentant des résistances mécaniques différentes et des compacités différentes. Ainsi, il est possible d'alléger certaines parties tandis que d'autres sont renforcées. Le compromis masse résistance mécanique peut être résolu indépendamment à différentes interfaces.The invention employs an annular flange with a material different from that of the annular wall. The material of the blade platforms is also different from that of the annular flange. These features offer a freedom of choice of materials with different mechanical strengths and different compacities. Thus, it is possible to lighten some parts while others are strengthened. The compromise mass resistance can be solved independently at different interfaces.

L'invention permet de réduire le nombre de feuilles de la préforme composite grâce à la diminution des contraintes mécaniques. Une conséquence est que la préforme est plus simple à réaliser puisque la difficulté de mise en oeuvre des feuilles tend à augmenter pour chaque feuille supplémentaire. Cette difficulté est amplifiée par les surfaces incurvées que présente couramment un carter. Une économie est réalisée sur les coûts de matière et de main d'oeuvre liés à la préforme.The invention makes it possible to reduce the number of sheets of the composite preform by reducing the mechanical stresses. One consequence is that the preform is simpler to achieve since the difficulty of implementation of the sheets tends to increase for each additional sheet. This difficulty is amplified by the surfaces curved that commonly presents a crankcase. An economy is realized on the costs of material and manpower related to the preform.

Brève description des dessinsBrief description of the drawings

  • La figure 1 représente une turbomachine axiale selon l'invention.The figure 1 represents an axial turbomachine according to the invention.
  • La figure 2 est un schéma d'un compresseur de turbomachine selon l'invention.The figure 2 is a diagram of a turbomachine compressor according to the invention.
  • La figure 3 illustre une coupe axiale d'une portion de carter suivant un premier mode de réalisation de l'invention.The figure 3 illustrates an axial section of a housing portion according to a first embodiment of the invention.
  • La figure 4 schématise une coupe axiale d'une portion de carter suivant un deuxième mode de réalisation de l'invention.The figure 4 schematizes an axial section of a housing portion according to a second embodiment of the invention.
  • La figure 5 illustre une vue depuis l'intérieur d'une bride annulaire selon le deuxième mode de réalisation de l'invention.The figure 5 illustrates a view from the inside of an annular flange according to the second embodiment of the invention.
  • La figure 6 ébauche une plateforme d'aube selon le deuxième mode de réalisation de l'invention.The figure 6 roughing a blade platform according to the second embodiment of the invention.
Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes intérieur ou interne et extérieur ou externe renvoient à un positionnement par rapport à l'axe de rotation d'une turbomachine axiale.In the following description, the terms inner or inner and outer or outer refer to a positioning relative to the axis of rotation of an axial turbomachine.

La figure 1 représente de manière simplifiée une turbomachine axiale. Il s'agit dans ce cas précis d'un turboréacteur double-flux. Le turboréacteur 2 comprend un premier niveau de compression, dit compresseur basse-pression 4, un deuxième niveau de compression, dit compresseur haute-pression 6, une chambre de combustion 8 et un ou plusieurs niveaux de turbines 10. En fonctionnement, la puissance mécanique de la turbine 10 transmise via l'arbre central jusqu'au rotor 12 met en mouvement les deux compresseurs 4 et 6. Des moyens de démultiplication peuvent augmenter la vitesse de rotation transmise aux compresseurs. Ou encore, les différents étages de turbines peuvent chacun être reliés aux étages de compresseur via des arbres concentriques. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stators. La rotation du rotor autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée de la chambre de combustion 10.The figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine. The turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6. Reducing means can increase the speed of rotation transmitted to the compressors. Or, the different turbine stages can each be connected to the compressor stages via concentric shafts. The latter comprise several rows of rotor blades associated with rows of stator vanes. Rotation of the rotor about its axis of rotation 14 thus allows to generate an air flow and to compress it gradually to the inlet of the combustion chamber 10.

Un ventilateur d'entrée communément désigné fan 16 est couplé au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 traversant les différents niveaux sus mentionnés de la turbomachine, et un flux secondaire 20 traversant un conduit annulaire (partiellement représenté) le long de la machine pour ensuite rejoindre le flux primaire en sortie de turbine. Les flux primaire 18 et secondaire 20 sont des flux annulaires, ils sont canalisés par le carter de la turbomachine. A cet effet, le carter présente des parois cylindriques ou viroles qui peuvent être internes ou externes.A commonly designated fan inlet fan 16 is coupled to the rotor 12 and generates a flow of air which is divided into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet. The primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine. For this purpose, the casing has cylindrical walls or ferrules which may be internal or external.

La figure 2 est une vue en coupe d'un compresseur d'une turbomachine axiale. Le compresseur peut être un compresseur basse-pression 4 tel que celui de la figure 1. On peut y observer une partie du fan 16 et le bec de séparation 22 du flux primaire 18 et du flux secondaire 20. Le rotor 12 comprend plusieurs rangées d'aubes rotoriques 24, en l'occurrence trois.The figure 2 is a sectional view of a compressor of an axial turbomachine. The compressor may be a low-pressure compressor 4 such as that of the figure 1 . There can be observed a portion of the fan 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20. The rotor 12 comprises several rows of rotor blades 24, in this case three.

Le compresseur 4 comprend plusieurs redresseurs, en l'occurrence quatre, qui contiennent chacun une rangée d'aubes statoriques 26. Les redresseurs sont associés au fan 16 ou à une rangée d'aubes rotoriques pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression.The compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26. The rectifiers are associated with the fan 16 or a row of rotor vanes to straighten the air flow, so that convert the speed of the flow into pressure.

Les aubes statoriques 26 s'étendent essentiellement radialement. Elles sont régulièrement espacées les unes des autres, et présentent une même orientation angulaire dans le flux. Avantageusement, les aubes 26 d'une même rangée sont identiques. Eventuellement, l'espacement entre les aubes peut varier localement tout comme leur orientation angulaire. Certaines aubes peuvent être différentes du reste des aubes de leur rangée.The stator vanes 26 extend essentially radially. They are regularly spaced from each other, and have the same angular orientation in the flow. Advantageously, the blades 26 of the same row are identical. Optionally, the spacing between the blades may vary locally as well as their angular orientation. Some blades may be different from the rest of the blades in their row.

Les aubes statoriques 26 présentent chacune un corps également appelé pale, s'étendant radialement en traversant la veine du flux primaire 18. Chaque aube présente également au moins une plateforme, éventuellement deux plateformes à savoir une plateforme externe 28 et une plateforme interne. Les plateformes délimitent radialement le flux primaire. Elles comprennent des surfaces de guidage aptes à guider ledit flux.The stator vanes 26 each have a body also called blade, extending radially through the vein of the primary flow 18. Each blade also has at least one platform, possibly two platforms, namely an external platform 28 and an internal platform. Platforms radially delineate the flow primary. They comprise guide surfaces capable of guiding said flow.

Le compresseur présente un carter annulaire externe 30. Le carter 30 enveloppe le compresseur. Il présente à cet effet une paroi annulaire 32 entourant la majorité des aubes rotoriques 24. La paroi annulaire 32 peut être formée de deux demi-coquilles formant chacune une moitié d'un tube découpé axialement. La paroi annulaire 32 présente une forme de tonneau ou d'ogive. Sa surface intérieure est concave. Sa variation de rayon est continue pour pouvoir compresser progressivement le flux.The compressor has an outer annular housing 30. The housing 30 envelopes the compressor. It has for this purpose an annular wall 32 surrounding the majority of the rotor blades 24. The annular wall 32 may be formed of two half-shells each forming a half of an axially cut tube. The annular wall 32 has a shape of barrel or ogive. Its inner surface is concave. Its radius variation is continuous to gradually compress the flow.

Le carter externe 30 est fixé en amont au bec de séparation 22, et est reçu par le carter intermédiaire 34 de la turbomachine en aval. Le carter intermédiaire 34 comprend une paroi annulaire interne et une paroi annulaire externe entre lesquelles s'étend radialement une rangée annulaire d'aubes ou de bras de carter. Le carter est essentiellement, préférentiellement uniquement relié au bec de séparation 22 et au carter intermédiaire. Le bec de séparation 22 peut uniquement être fixé sur le carter externe 30 de sorte à être son support unique.The outer casing 30 is attached upstream to the separation spout 22, and is received by the intermediate casing 34 of the downstream turbomachine. The intermediate casing 34 comprises an inner annular wall and an outer annular wall between which radially extends an annular row of blades or casing arms. The casing is essentially, preferably only connected to the separation spout 22 and the intermediate casing. The separation spout 22 can only be fixed to the outer casing 30 so as to be its sole support.

Le carter extérieur 30 comprend également une bride annulaire radiale, préférentiellement deux brides annulaires 36. Le carter extérieur 30 est fixé au bec de séparation 22 et au carter intermédiaire 34 par l'intermédiaire de ses brides annulaires 36. Le carter extérieur 30 comprend une bride annulaire amont et une bride annulaire aval. Chacune d'elle peut former un demi-cercle. Préférentiellement, chaque demi-cercle coïncide avec une demi-coquille du carter extérieur 30.The outer casing 30 also comprises a radial annular flange, preferably two annular flanges 36. The outer casing 30 is fixed to the partition spout 22 and to the intermediate casing 34 via its annular flanges 36. The outer casing 30 comprises a flange annular upstream and a downstream annular flange. Each of them can form a semicircle. Preferably, each semicircle coincides with a half-shell of the outer casing 30.

Le carter extérieur 30 comprend également des couches annulaires de matériau abradable 38. Ces couches d'abradable 38 sont disposées axialement au droit des aubes rotoriques 24. Elles s'étendent axialement entre les plateformes externes 28 des aubes statoriques 26.The outer casing 30 also comprises annular layers of abradable material 38. These abradable layers 38 are arranged axially in line with the rotor vanes 24. They extend axially between the outer platforms 28 of the stator vanes 26.

La figure 3 est une vue en coupe d'un carter extérieur 30 de compresseur d'une turbomachine axiale 2 tel que celle de la figure 1. L'enseignement de l'invention pourrait également être appliqué à un carter de turbine, de chambre de combustion ou encore à un carter intermédiaire. Le carter peut être un carter extérieur ou un carter intérieur qui délimite l'extérieur, respectivement l'intérieur d'un flux annulaire. Le carter représenté montre une des aubes statoriques 26 et une portion de la bride annulaire 36.The figure 3 is a sectional view of an outer compressor casing 30 of an axial turbomachine 2 such as that of the figure 1 . The teaching of the invention could also be applied to a turbine casing, a combustion chamber or an intermediate casing. The casing may be an outer casing or an inner casing which delimits the outside, respectively inside an annular flow. The casing shown shows one of the stator vanes 26 and a portion of the annular flange 36.

La paroi annulaire 32 comprend des premiers moyens de fixation. Les premiers moyens de fixation peuvent comprendre des orifices traversants qui forment au moins une rangée annulaire. Les premiers moyens de fixation peuvent comprendre un premier jeu de moyens de fixation disposés annulairement et un deuxième jeu de moyens de fixation disposés annulairement. Le premier jeu est chevauché axialement par la bride annulaire, le deuxième jeu étant chevauché axialement par la plateforme. Les premiers moyens de fixation peuvent comprendre d'autres jeux de moyens de fixation qui sont chevauchés et coopèrent avec une autre bride annulaire radiale et/ou avec d'autres rangées annulaires d'aubes.The annular wall 32 comprises first fixing means. The first fastening means may comprise through orifices which form at least one annular row. The first fastening means may comprise a first set of fastening means arranged annularly and a second set of fastening means arranged annularly. The first set is axially overlapped by the annular flange, the second set being axially overlapped by the platform. The first fastening means may comprise other sets of fastening means which are overlapped and cooperate with another radial annular flange and / or with other annular rows of vanes.

La paroi annulaire 32 est en matériau composite. Le matériau composite peut comprendre une matrice organique. La matrice peut être réalisée à partir d'une résine organique injectée dans un moule puis qui polymérise. Le procédé d'injection peut être un procédé de transfert, connu sous l'acronyme RTM (Resin Transfert Molding en anglais). Préférentiellement la résine est thermodurcissable. Elle peut être une résine époxy.The annular wall 32 is made of composite material. The composite material may comprise an organic matrix. The matrix can be made from an organic resin injected into a mold and then polymerizing. The injection process may be a transfer method, known by the acronym RTM (Resin Transfer Molding). Preferably, the resin is thermosetting. It can be an epoxy resin.

Le matériau composite comprend une préforme. Cette dernière peut être formée d'un empilement de plis ou feuilles de fibres. Les feuilles peuvent être des feuilles avec des fibres de verre et/ou des feuilles avec des fibres de carbone. Les fibres sont des fibres longues. Les fibres peuvent être des fibres ordonnées et/ou des fibres agencées de manière aléatoire. Les fibres être tissées. Elles peuvent être pré-imprégnées d'une résine. La préforme comprend un empilement de 5 à 40 feuilles, préférentiellement de 8 à 20 feuilles, plus préférentiellement de 10 à 15 feuilles. Le nombre de couches formées par les feuilles peut varier localement de sorte à renforcer localement le carter, par exemple au niveau des zones de fixation.The composite material comprises a preform. The latter may be formed of a stack of folds or sheets of fibers. The sheets can be sheets with glass fibers and / or sheets with carbon fibers. The fibers are long fibers. The fibers may be ordered fibers and / or randomly arranged fibers. The fibers are woven. They can be pre-impregnated with a resin. The preform comprises a stack of 5 to 40 leaves, preferably 8 to 20 leaves, more preferably 10 to 15 leaves. The number of layers formed by the sheets may vary locally so as to locally reinforce the housing, for example at the fixing areas.

La bride annulaire 36 est réalisée en un matériau différent de la paroi annulaire 32. Elle peut être réalisée en un matériau métallique. Elle peut être réalisée en titane, en aluminium ou en acier. La bride annulaire peut être réalisée en un matériau composite, par exemple à matrice céramique et/ou avec des fibres métalliques. Les matrices et les fibres présentées précédemment peuvent également être employées.The annular flange 36 is made of a material different from the annular wall 32. It may be made of a metallic material. It can be made of titanium, aluminum or steel. The ring flange can be made of a composite material, for example ceramic matrix and / or with metal fibers. The matrices and fibers presented above can also be used.

La bride annulaire 36 présente généralement un profil en « L ». Le profil présente une portion radiale 40 et une portion axiale 42. Le profil présente généralement une épaisseur constante, son épaisseur varie de moins de 20% par rapport à son épaisseur moyenne. La portion axiale 42 peut être inclinée par rapport à l'axe de rotation de la turbomachine. La portion axiale 42 présente une surface d'appui épousant la surface intérieure de l'extrémité de la paroi annulaire 32.The annular flange 36 generally has an "L" profile. The profile has a radial portion 40 and an axial portion 42. The profile generally has a constant thickness, its thickness varies less than 20% relative to its average thickness. The axial portion 42 may be inclined relative to the axis of rotation of the turbomachine. The axial portion 42 has a bearing surface conforming to the inner surface of the end of the annular wall 32.

La surface intérieure de la paroi annulaire 32 comprend une zone annulaire de réception 43 des plateformes de aubes 26. La zone annulaire de réception 43 peut avoir un profil radial rectangulaire, ou sensiblement en forme de trapèze de sorte à permettre l'insertion des plateformes depuis l'intérieur. La bride annulaire 36 peut délimiter directement la zone annulaire de réception 43. Préférentiellement, il s'agit de la portion axiale 42 qui délimite la zone annulaire de réception 43. A cet effet, elle présente un bord 44 annulaire amont qui délimite la zone de réception 43. La paroi annulaire 32 comprend une zone annulaire de réception d'un matériau abradable 37. La zone de réception des plateformes 43 peut être délimitée par la zone annulaire de réception d'un matériau abradable 37. Elle peut également l'être par le bord 44 de la portion de bride s'étendant axialement 42. Avantageusement la couche annulaire d'abradable 38 est logée dans la zone annulaire de réception d'un matériau abradable 37.The inner surface of the annular wall 32 comprises an annular receiving zone 43 of the blade platforms 26. The annular receiving zone 43 may have a rectangular radial profile, or substantially trapezoidal shape so as to allow the insertion of the platforms from inside. The annular flange 36 may define directly the annular receiving zone 43. Preferably, it is the axial portion 42 which delimits the annular receiving zone 43. For this purpose, it has an upstream annular edge 44 which delimits the zone of The annular wall 32 comprises an annular zone for receiving an abradable material 37. The reception zone of the platforms 43 may be delimited by the annular zone for receiving an abradable material 37. It may also be the edge 44 of the axially extending flange portion 42. Advantageously, the annular abradable layer 38 is housed in the annular zone for receiving an abradable material 37.

La bride annulaire 36 est fixée à l'extrémité de la paroi annulaire 32 via sa portion axiale 42. Cette dernière présente à cet effet des deuxièmes moyens de fixation 45 qui coopèrent avec des premiers moyens de fixation de la paroi. Les deuxièmes moyens de fixation 45 peuvent être des axes s'étendant généralement radialement, préférentiellement de manière orthogonale à l'interface entre la paroi annulaire 32 et la portion axiale 42. Les axes peuvent être des lockbolts ou des vis. Ils sont montés sur la bride annulaire une fois qu'elle est plaquée contre la paroi annulaire.The annular flange 36 is fixed to the end of the annular wall 32 via its axial portion 42. The latter has for this purpose second fastening means 45 which cooperate with first means for fixing the wall. The second fixing means 45 may be axes extending generally radially, preferably orthogonal to the interface between the annular wall 32 and the axial portion 42. The axes may be lockbolts or screws. They are mounted on the annular flange once it is pressed against the annular wall.

La portion radiale 40 du profil de la bride annulaire 36 génère par rotation autour de l'axe de rotation 14 un plan perpendiculaire 46 à ce même axe. Des moyens de montage 48 peuvent être placés sur la portion radiale 40. Les moyens de montage 48 peuvent être des orifices destinés à recevoir des vis de fixation qui coopèrent avec le carter intermédiaire. Les deuxièmes moyens 45 de fixation peuvent être moins espacés les uns des autres que les moyens de montage 48.The radial portion 40 of the profile of the annular flange 36 generates by rotation about the axis of rotation 14 a perpendicular plane 46 to the same axis. Mounting means 48 may be placed on the radial portion 40. The mounting means 48 may be openings for receiving fastening screws which cooperate with the intermediate casing. The second fixing means 45 may be less spaced apart from each other than the mounting means 48.

Le profil de la bride annulaire comprend de manière optionnelle une portion de jonction 50 entre la portion axiale 42 et la portion radiale 40. La portion de jonction 50 peut présenter une forme de marche. La forme de marche peut ménager un jeu axial 52 au niveau de l'extrémité axiale de la paroi annulaire 32. Le jeu 52 peut être nul de sorte à assurer un appui. Préférentiellement la forme de marche fait saillie vers l'extérieur. La surface intérieure de la zone de jonction 50 peut générer par rotation une surface cylindrique 54. Cette surface cylindrique 54 peut former un emmanchement arbre alésage avec le bec de séparation, le carter intermédiaire, ou avec tout autre élément auquel la bride annulaire 36 est fixée.The profile of the annular flange optionally comprises a joining portion 50 between the axial portion 42 and the radial portion 40. The joining portion 50 may have a step shape. The step form may provide an axial clearance 52 at the axial end of the annular wall 32. The clearance 52 may be zero so as to provide support. Preferably the step form protrudes outwardly. The inner surface of the junction zone 50 may rotatably generate a cylindrical surface 54. This cylindrical surface 54 may form a bore shaft bore with the partition spout, intermediate housing, or any other element to which the annular flange 36 is attached. .

L'aube 26 comporte des troisièmes moyens de fixation 56 pour la monter sur la paroi annulaire 32. Les troisièmes moyens de fixation 56 coopèrent avec les premiers moyens de fixation de la paroi annulaire. Les troisièmes moyens de fixation 56 s'étendent radialement depuis la plateforme 28 dans une direction opposée à la pale de l'aube 26. Les troisèmes moyens de fixation 56 peuvent traverser la paroi annulaire 32. La plateforme 28 épouse généralement la surface intérieure de la paroi annulaire. La plateforme présente une surface d'appui qui est généralement plaquée contre la paroi annulaire, éventuellement seul le contour de la surface d'appui est en contact de la paroi annulaire.The blade 26 has third fixing means 56 for mounting it on the annular wall 32. The third fastening means 56 cooperate with the first fixing means of the annular wall. The third attachment means 56 extend radially from the platform 28 in a direction opposite to the blade of the blade 26. The third attachment means 56 can pass through the annular wall 32. The platform 28 generally marries the inner surface of the annular wall. The platform has a bearing surface which is generally pressed against the annular wall, possibly only the contour of the bearing surface is in contact with the annular wall.

La plateforme 28 est en contact de la portion axiale 42 de la bride annulaire. Elles butent axialement l'une contre l'autre. Puisque la paroi annulaire est inclinée à cet endroit, la plateforme et la portion axiale de la bride annulaire permettent également une transmission d'effort orienté radialement. La bride annulaire et la paroi annulaire sont en contact au niveau de la partie axiale 42. Cette zone de contact est étendue et permet également une transmission d'efforts axiaux et radiaux.The platform 28 is in contact with the axial portion 42 of the annular flange. They abut axially against each other. Since the annular wall is inclined at this point, the platform and the axial portion of the annular flange also allow radially oriented transmission of force. The annular flange and the annular wall are in contact with the level of the axial portion 42. This contact area is extended and also allows transmission of axial and radial forces.

La jonction 58 entre la portion axiale 42 et la plateforme 28 est lisse. A cet endroit, les épaisseurs de la portion axiale et de la bride annulaire sont égales de sorte à ne pas perturber les écoulements. Pour éviter qu'il y ait chevauchement, le profil de l'interface s'étend perpendiculairement à la surface de la paroi annulaire. Les deux éléments sont en contact sur toute leur épaisseur pour favoriser la transmission des efforts.The junction 58 between the axial portion 42 and the platform 28 is smooth. At this point, the thicknesses of the axial portion and the annular flange are equal so as not to disturb the flow. To avoid overlap, the profile of the interface extends perpendicularly to the surface of the annular wall. The two elements are in contact over their entire thickness to promote the transmission of efforts.

La figure 4 représente un carter 130 selon un deuxième mode de réalisation de l'invention. Cette figure 4 reprend la numérotation des figures précédentes pour les éléments identiques ou similaires, la numération étant toutefois incrémentée de 100. Des numéros spécifiques sont utilisés pour les éléments spécifiques à ce mode de réalisation.The figure 4 represents a housing 130 according to a second embodiment of the invention. This figure 4 resumes the numbering of the preceding figures for identical or similar elements, however, the numbering is incremented by 100. Specific numbers are used for the specific elements of this embodiment.

La portion de jonction 150 présente un profil rectiligne. Le profil de la portion de jonction est incliné par rapport aux profils de la portion axiale et de la portion radiale. La longueur de la portion axiale 142 est supérieur à la longueur de la plateforme 128. La portion axiale dépasse la plateforme en amont et en aval.The joining portion 150 has a straight profile. The profile of the joining portion is inclined relative to the profiles of the axial portion and the radial portion. The length of the axial portion 142 is greater than the length of the platform 128. The axial portion extends beyond the platform upstream and downstream.

La bride annulaire 136 présente une cavité radiale 160 dans laquelle est introduite la plateforme 128 de l'aube 126. La cavité radiale 160 peut être ménagée sur la surface intérieure de la portion axiale lorsque cette dernière est placée à l'intérieur de la paroi annulaire. Suivant une autre configuration, la cavité radiale 160 peut être ménagée sur la surface extérieure si la portion axiale est placée à l'extérieur de la paroi annulaire. L'aube 126 est montée sur la bride annulaire 136 en insérant sa plateforme 128 dans la cavité radiale 160 depuis l'intérieur.The annular flange 136 has a radial cavity 160 in which is introduced the platform 128 of the blade 126. The radial cavity 160 may be formed on the inner surface of the axial portion when the latter is placed inside the annular wall . According to another configuration, the radial cavity 160 may be formed on the outer surface if the axial portion is placed outside the annular wall. The blade 126 is mounted on the annular flange 136 by inserting its platform 128 into the radial cavity 160 from the inside.

La plateforme 128 présente une zone centrale 162 épousant le fond de la cavité radiale 160. Elle présente également des zones de moindre épaisseur 164 disposées axialement de part et d'autre la zone centrale 162. Les zones de moindre épaisseur 164 peuvent être en retrait du fond de la cavité radiale 160.The platform 128 has a central zone 162 conforming to the bottom of the radial cavity 160. It also has thinner zones 164 arranged axially on either side of the central zone 162. The zones of smaller thickness 164 may be set back from the bottom of the radial cavity 160.

Dans cette configuration, les troisièmes moyens de fixation 156 de l'aube, les deuxièmes moyens de fixation de la bride annulaire, et les premiers moyens de fixation de la paroi annulaire coïncident. Les troisièmes moyens de fixation 156 coopèrent à la fois avec les premiers moyens de fixation et les deuxièmes moyens de fixation. Les orifices formés dans la bride annulaire et les orifices formés aux extrémités de la paroi annulaire sont mis en correspondance. L'axe de fixation 156 de l'aube traverse l'orifice de fixation de la paroi annulaire ainsi que l'orifice de fixation de la bride annulaire. Cette solution permet de simplifier l'assemblage du carter 130 puisque les troisièmes moyens de fixation des aubes sont utilisés à la fois pour fixer la bride annulaire et la paroi annulaire. Ceci permet d'alléger le carter. Une économie de moyens de fixation est réalisée. L'assemblage du carter est accéléré.In this configuration, the third attachment means 156 of the blade, the second fixing means of the annular flange, and the first fastening means of the annular wall coincide. The third attachment means 156 cooperate with both the first attachment means and the second attachment means. The orifices formed in the annular flange and the orifices formed at the ends of the annular wall are matched. The attachment axis 156 of the vane passes through the fixing orifice of the annular wall and the fixing orifice of the annular flange. This solution simplifies the assembly of the housing 130 since the third blade attachment means are used both for fixing the annular flange and the annular wall. This allows to lighten the crankcase. An economy of fastening means is achieved. The crankcase assembly is accelerated.

La bride annulaire 136 présente également un prolongement axial 166. Le prolongement axial 166 s'étend depuis la portion de jonction 150 dans un sens opposé à la portion axiale 142. Le prolongement axial peut s'étendre juqu'au droit de la surface aval de la portion radiale 140. Il peut servir de buté axiale.The annular flange 136 also has an axial extension 166. The axial extension 166 extends from the junction portion 150 in a direction opposite to the axial portion 142. The axial extension may extend up to the right of the downstream surface. the radial portion 140. It can serve as an axial stop.

La figure 5 représente la surface de guidage de la bride annulaire selon le deuxième mode de réalisation de l'invention.The figure 5 represents the guide surface of the annular flange according to the second embodiment of the invention.

La bride annulaire 136 montre une pluralité de cavités radiales 160. Les cavités radiales sont disposées annulairement. Elles sont réparties sur la surface interne de la bride annulaire 136. Les cavités radiales 160 sont identiques. Elle présentent chacune un deuxième moyen de fixation. Une plateforme 128 d'aube 126 est représentée introduite dans une cavité radiale.The annular flange 136 shows a plurality of radial cavities 160. The radial cavities are arranged annularly. They are distributed on the inner surface of the annular flange 136. The radial cavities 160 are identical. They each have a second fixing means. A platform 128 of blade 126 is shown introduced into a radial cavity.

Chaque cavité radiale 160 reçoit une plateforme d'aube 128. La longueur de la cavité radiale est ajustée à la longueur de la plateforme de sorte à caler axialement la plateforme dans le carter.Each radial cavity 160 receives a blade platform 128. The length of the radial cavity is adjusted to the length of the platform so as to axially wedge the platform in the housing.

Le fond de chaque cavité radiale 160 présente une partie centrale 168 et deux parties latérales 170 disposées axialement dans le prolongement de la partie centrale 168. Ces parties sont planes. Chaque partie latérale est inclinée par rapport à la partie centrale vers l'extérieur de la cavité correspondante.The bottom of each radial cavity 160 has a central portion 168 and two lateral portions 170 arranged axially in the extension of the central portion 168. These parts are flat. Each side portion is inclined relative to the central portion outwardly of the corresponding cavity.

La figure 6 représente une plateforme 128 d'aube 126 selon le deuxième mode de réalisation de l'invention. Eventuellement, ce modèle de plateforme peut être employé dans d'autres modes de réalisation de l'invention.The figure 6 represents a platform 128 of dawn 126 according to the second embodiment of the invention. Optionally, this platform model may be employed in other embodiments of the invention.

La plateforme 128 présente une forme généralement rectangulaire. Elle présente deux côté longitudinaux 172 opposés et disposés selon l'axe de rotation de la turbomachine, ainsi que deux côtés transversaux 174 opposés qui sont agencés perpendiculairement à l'axe de rotation de la turbomachine.The platform 128 has a generally rectangular shape. It has two longitudinal sides 172 opposite and arranged along the axis of rotation of the turbomachine, and two opposite transverse sides 174 which are arranged perpendicularly to the axis of rotation of the turbomachine.

La partie centrale 162 de la plateforme présente une forme générale de disque. Le disque peut être tronqué, éventuellement des deux côtés longitudinaux 172. Les troisièmes moyens de fixation 156 sont avantageusement centrés sur la partie centrale 162. Réaliser une plateforme avec une surface d'appui réduite permet de réduire la surface de frottement entre la plateforme et la bride annulaire. Cela facilite le positionnement angulaire de l'aube. Aussi, les zones de moindre épaisseur 164 permettent d'alléger l'aube.The central portion 162 of the platform has a general shape of disc. The disk may be truncated, possibly on both longitudinal sides 172. The third attachment means 156 are advantageously centered on the central portion 162. Creating a platform with a reduced bearing surface makes it possible to reduce the friction surface between the platform and the annular flange. This facilitates the angular positioning of the dawn. Also, the smaller areas 164 can lighten the dawn.

Claims (15)

  1. Housing (30; 130) of an axial turbomachine (2), in particular of a compressor (4; 6), comprising:
    - an annular row of blades extending radially and each comprising a respective platform (28; 128);
    - an annular wall (32; 132) of composite material and whose inner surface comprises an annular area (43; 143) for receiving the platforms (28, 128) of the row of blades (26; 126),
    - at least one annular flange (36; 136) extending radially and comprising an axial portion (42; 142),
    characterized in that
    the annular flange (36; 136) is attached to the annular wall (32; 132) and bounds the receiving area (43; 143) of the platforms (28; 128) of the blades through an axial contact between the axial portion (42; 142) of the annular flange (36; 136) and the platforms (28; 128).
  2. Housing (30; 130) according to claim 1, characterized in that the radial section of the annular flange (36; 136) has an L-shaped profile, the profile having an axially extending part (42; 142) and a radially extending part (40; 140), the axially extending part (42; 142) being preferably located mainly radially on the side of the inner surface of the annular wall, and the radially extending part (40; 140) being located mainly radially on the side of the outer surface of the annular wall.
  3. Housing (30) according to claim 2, characterized in that the part (42) of the flange (36) extending axially comprises an edge (44) bounding the receiving area (43; 143) of the blade platforms.
  4. Housing (30) according to claim 3, characterized in that the annular wall (32) comprises an annular area for receiving an abradable material (37; 137), the receiving area of the platforms (43; 143) being bounded, on one side, by the said receiving area of an abradable material (37; 137) and, on the other side, by the edge (44; 144) of the axially extending part (42) of the flange.
  5. Housing (30) according to claims 1 to 4, characterized in that the receiving area of the platforms (28) of the blades (26) forms an annular recess, the radial section of the annular recess preferably being substantially rectangular and designed to permit radial insertion of the platforms (28) of the blades (26).
  6. Housing according to claims 1 to 5, characterized in that the annular wall (32; 132) and the annular flange (36; 136) are made of different materials, the annular flange (36; 136) being preferably made of a metallic material.
  7. Housing according to claims 1 to 6, characterized in that the composite annular wall (32; 132) comprises an organic matrix and a preform comprising fibres, the matrix being preferably homogeneously distributed over the annular wall (32; 132).
  8. Housing according to claims 1 to 7, characterized in that the annular wall (32, 132) comprises a first means of fixing, the annular flange (36; 136) includes a second means of fixing (45) and the blades (26; 126) comprise a third means of fixing (56; 156), the first means of fixing interacting with the second means of fixing, and/or the third means of fixing interacting with both the first means of fixing and the second means of fixing.
  9. Housing (130) according to claim 8, characterized in that the third means of fixing (156) extend radially through the annular wall and the annular flange, the third means of fixing (156) preferably comprising clamping means, possibly reversible.
  10. Housing (30; 130) according to claims 1 to 9, characterized in that the contour of each platform (28; 128) has longitudinal edges (172) and transverse edges (174), at least one of the said edges being in contact with the annular flange (36; 136), the flange thus ensuring that the platforms are locked against rotating.
  11. Housing (30; 130) according to claims 1 to 10, characterized in that the platforms (28; 128) and the annular flange (36; 136) each comprise a guidance surface designed to guide the flow (18; 20) in a turbomachine (2), the guidance surfaces of the platforms lying flush with the guidance surface of the annular flange (36; 136).
  12. Housing (130) according to claims 1 to 11, characterized in that the annular flange (136) comprises a part which follows a surface, preferably interior, of the annular wall (132), the said part extending axially over more than half of the receiving area of the platforms (128) of the blades (126).
  13. Housing (130) according to claims 1 to 12, characterized in that the annular flange (136) includes radial recesses (160) designed for the reception of platforms (128) of the blades (126), the radial recesses (160) preferably being configured to be largely open towards the bodies of the blades (126).
  14. Housing (130) according to claims 1 to 13, characterized in that the platforms (128) have each a generally disc-shaped central region (162), and two areas of reduced thickness (164) located axially on either side of the central region (162), the central region (162) predominantly bearing radially against the annular flange (136) and at least one of the areas of reduced thickness abutting predominantly axially against the annular flange (136).
  15. Axial turbomachine (2) housing, comprising a housing (30, 130), characterized in that the housing (30, 130) is in accordance with one of claims 1 to 14, the housing preferably being an external annular housing and comprising an upstream annular flange (36, 136) and a downstream annular flange (36, 136).
EP13170209.4A 2013-06-03 2013-06-03 Composite casing for axial turbomachine compressor with metal flange Active EP2811121B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP13170209.4A EP2811121B1 (en) 2013-06-03 2013-06-03 Composite casing for axial turbomachine compressor with metal flange
CA2852180A CA2852180A1 (en) 2013-06-03 2014-05-21 Composite housing with a metallic fixing flange for the compressor of an axial turbomachine
US14/285,013 US20150192140A1 (en) 2013-06-03 2014-05-22 Composite Housing with a Metallic Flange for the Compressor of an Axial Turbomachine
RU2014121327A RU2674808C2 (en) 2013-06-03 2014-05-27 Composite material casing with metal fastening flange for axial-flow turbomachine compressor
CN201410235799.2A CN104213947B (en) 2013-06-03 2014-05-30 The housing of axial flow turbo-machine and the axial flow turbo-machine including the housing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13170209.4A EP2811121B1 (en) 2013-06-03 2013-06-03 Composite casing for axial turbomachine compressor with metal flange

Publications (2)

Publication Number Publication Date
EP2811121A1 EP2811121A1 (en) 2014-12-10
EP2811121B1 true EP2811121B1 (en) 2019-07-31

Family

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EP13170209.4A Active EP2811121B1 (en) 2013-06-03 2013-06-03 Composite casing for axial turbomachine compressor with metal flange

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US (1) US20150192140A1 (en)
EP (1) EP2811121B1 (en)
CN (1) CN104213947B (en)
CA (1) CA2852180A1 (en)
RU (1) RU2674808C2 (en)

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BE1022497B1 (en) * 2014-06-05 2016-05-12 Techspace Aero S.A. MOLD FOR ABRADABLE TRACK UNDER INTERNAL VIROL OF AXIAL TURBOMACHINE COMPRESSOR
US9938840B2 (en) * 2015-02-10 2018-04-10 United Technologies Corporation Stator vane with platform having sloped face
BE1023290B1 (en) * 2015-07-22 2017-01-24 Safran Aero Boosters S.A. AUBE COMPOSITE COMPRESSOR OF AXIAL TURBOMACHINE
US20180017074A1 (en) * 2016-07-13 2018-01-18 General Electric Company System and method for reduced stress vane shroud assembly
CN107642504B (en) * 2017-09-30 2019-08-23 中国航发沈阳发动机研究所 The fancase of Screw assembly
US11028709B2 (en) * 2018-09-18 2021-06-08 General Electric Company Airfoil shroud assembly using tenon with externally threaded stud and nut
FR3087827B1 (en) * 2018-10-25 2020-10-09 Safran Aircraft Engines BLOWER HOUSING IN COMPOSITE MATERIAL INCLUDING METAL FLANGES
FR3094906B1 (en) * 2019-04-12 2022-06-10 Safran Aircraft Engines METHOD FOR MANUFACTURING A STATOR BLADE ELEMENT FOR A TURBOMACHINE AND TOOLS FOR ITS IMPLEMENTATION
US10975730B2 (en) 2019-07-02 2021-04-13 Raytheon Technologies Corporation Duct assembly for a gas turbine engine

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US5226789A (en) * 1991-05-13 1993-07-13 General Electric Company Composite fan stator assembly
US7278821B1 (en) * 2004-11-04 2007-10-09 General Electric Company Methods and apparatus for assembling gas turbine engines
GB2434182A (en) * 2006-01-11 2007-07-18 Rolls Royce Plc Guide vane arrangement for a gas turbine engine
EP2075416B1 (en) * 2007-12-27 2011-05-18 Techspace Aero Method for manufacturing a turboshaft engine element and device obtained using same
EP2402615B1 (en) 2010-06-29 2015-08-12 Techspace Aero S.A. Axial compressor diffuser architecture

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US4063847A (en) * 1974-08-23 1977-12-20 Rolls-Royce (1971) Limited Gas turbine engine casing

Also Published As

Publication number Publication date
EP2811121A1 (en) 2014-12-10
RU2674808C2 (en) 2018-12-13
CA2852180A1 (en) 2014-12-03
RU2014121327A (en) 2015-12-10
CN104213947A (en) 2014-12-17
CN104213947B (en) 2018-05-29
US20150192140A1 (en) 2015-07-09

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